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Oct. 1, 1929. P. BARLow ET AL COOLING SYSTEM FOR INTERNAL COMBUSTION ENGINES Filed March 16, 1928 /Nvs/v To .QS

way. ma. 4 rra/uws? AVM Patented Oct'. 1, 1929 UNITED STATES PATENT OFFICE LESTER P. IBARLOW, OF DETROIT, MICHIGAN, AND ROBERT G. BREENE, OF DAYTON,

OHIO v COOLING SYSTEM FOR INTERNAL-COMBUSTION ENGINES Application filed March 16, 1928.y Serial No. 262,068.

This invention relates in general to aeronautics, vand is more particularly concerned with cooling systems of internal combustion engines for airplanes or other aircraft having aerofoil surfaces.

The invention has for its object the'provision of a steam cooling system for such engines, so constructed and arranged as to provide efficient cooling of the engine under all conditions of service, and which accomplishes this result Without the manifest disadvantages inherent in the use of water cooling systems. l

Another object of our invention is to so arrange our vapor condenser that it will serve to tend to prevent the formation of ice thereon while the craft is passing through snow and sleet and at `the same time provide a condenser perfectly streamlined with the aircraft.

With these objects in view, this invention consists of the novel construction of the cooling system, in the steam or vapor condenser, and in the connections and parts.

It is a further, and most important object of our invention to provide a steam cooling means in which the condenser and its component parts are arranged without any additional head resistance to the aircraft and one which presents the minimum of vulnerability to hostile aircraft or ground fire.

The invention further consists of certain arrangements and combinations of parts, all of which will be first fully described and afterwards specifically pointed out in the appended claims.

' Referring to the accompanying drawing:

Figure l is a view partly in side elevation and partly in vertical section illustratin the cooling system in operative position, an

Figure 2 is a fragmentary view of an airplane wing partly in section and illustrating the steam or vapor condenser in the wing of a pursuit airplane. t

Figure 3 is a detail in section showing a portion of our condensing chamber.

Like, numerals of references indicatejthe same paits throughout the figures, in which: 1 indicates an internal combustion engine partly in section to illustrate the cylinders 2.-

3 is a manifold over the cylinder heads and connecting with the water jackets 4. The manifold 3 includes a nipple or other suitable end 5 to receive the tube or pipe 6, flexible or otherwise, and an enlarged downwardly depending 'portion 7 formed to reenter the water jacket 4 at the extreme bottom thereof.

Applied to this depending portion 7 in the usual manner is a gage glass 8 having two prominent calibrations 9 thereon, between which the level" of the water in the motor 1 and manifold should be maintained for most efficient operation of the system.

10 indicates the wing 1 or other aerofoil of an airplane, within the interior of which we position an elongated steam or vapor receiv ing tank 11 to which the tube or pipe 6 is connected as by means of a nipple 12 terminating at 13 above the bottom of the tank 11, as shown lin the drawing. From the bottom of the said tank l1 at the front and rear thereof, we provide suitable drain pipes 14 and 15 which may merge at 16, into a single pipe 17 and connect to the bottom of the depending portion 7 of the manifold 3.

The whole or a suitable portion of the interior of the wing or aerofoil 10 may be employed as a condensing chamber 18, the size and extent of this chamber depending on size and type of the aircraft and its power plant.

Projecting laterally from each side of the receiving tank 11 and near the top thereof are a plurality of condensing pipes 19, the length of which pipes is coincident with the length of the condensing chamber 18, as will appear from Figure 2. The said pipes 19` are provided along their upper surfaces with a series of pcrforations 20 through which the steam or 'vapor passes into the condensing chamber 18.

Under some conditions, we may find it advisable to supply over cach row of perforations, considered longitudinally of the craft, an 11p-raised corrugation in the surface 21 to receive and deflect the steam or vapor as it passes intovthe condensing chamber 18. In some installations this may not be necessary. In fact it is to be understood that the construction and arrangement of the parts of the entire system may be changed or altered with the scope of the invention in order to meet conditions and requirements as they are found to exist.

Positioned preferably below the chassis of -the alrplane or otherwise conveniently placed 1s an a1r driven circulating pump 22 connected to a small vented drain tank 23, within a stream-lined shell 24. In some cases this drain tank will be incorporated in an airfoil surface or other streamlinedportion of the aircraft landing gear.

Connecting the condensing chamber 18 with the drain tank 23 are one or more drain pipes 25 leading from the drain ports 30, see. Flgure 2, while the pump 22 is piped to the bottom of the depending portion 7 in order to deliver to the engine water jacket the contents of the said drain tank 23 as it passes j thereto from the condensing chamber 18.

Connected also to the said depending portion 7 of the manifold 3 by a pipe 26 is a water supply tank 27, the contents of which are supplied to the engine water jacket by aconduit 28, controlled by a manually controlled valve 28a, in order to maintain the proper level within the same as indicated by the gage 8.

Having thus fully described the invention, its operation will be seen to be as follows:

Water being supplied to the water jacket of the engine to the 'desired level as indicated by the gage glass 28, the steam and vapor therefrom is deliveredto the receiving tank 11 in the wing or aerofoil 10. Such water as accompanies the steam and vapor is separated either by the action of the de'lector 30 into the manifold portion 7 or is carried into the receiving tank 11 and there separated. Such water as reaches the tank 11 is immediately returned, together with the condensate of the steam condensed in said tank, to the engine water jacket through the drain pipes 14 and 15. The uncondensed steam passing from the receiving tank 11 into the projecting condensing pipes 19 is now quite dry. The substantially dry steam and vapor passes from the condensing pipes 19 through the perf`orations 20 and into the condensing chamber 18 where the final condensation takes place andthe condensate therefrom passes throughthe drains 25, preferably led alongand streamlined with the adjacent struts, to the 'drain tank 23 whence it is returned to the engine water jacket 4 by the circulating pump 22. Atv31 we have disclosed an additional'circulating pump for forcing the cooling water through the cylinder jackets at a comparatively high velocity. This provision eliminates the necessitv of large capacity water jackets and increases the etliciency of our heat transfer system.V rlFhis pump may be dispensed with, if desired in` some types of engines.

Having thus fully described the invention -we do not wish to be understood as limiting ourselves to the exact construction herein set forth as the same is susceptible to various changes in the construction and arrangement of the component parts ofthe system without departing from the spirit of the invention, and we consider ourselves clearly entitled to all such changes and modifications as fall within the limitl and scope of the appended claims.

We claim: i

v1. A device of the character described including, in combination with the water jacket of an internal combustion engine, a manifold above the water acket, said manifold including a depending portion for connection with the water jacket at the bottom thereof, a steam and vapor receiving tank disposed internally of an airplane wing or aerofoil of an aircraft, means for connecting the manifold with the receiving tank to deliver into the receiving tank the steam and vapor from the water jacket, a series of perforated condensing pipes projecting from eachside of the receiving tank into a condensing chamber within the wing or airfoil, longitudinally extending corrugations over the perforations in the condensing pipes, a vented drain tank,

means connecting the condensing chamber with the/drain tank to drain the condensate from the condensing chamber, a wind driven circulating pump for returning the contents of the drain tank to the engine water jacket,

means for draining the condensate of the receiving tank into the waterjacket, a supply tank communicating with the water jacket,

means for delivering the contents of the sup- 'ply tank to the water jacket, and a gage-glass on the depending portion of the manifold for indicating the Water level within the depending manifold.

2. A device of the character described including, in combination with the water acket of an internal combustion engine, a mani: fold above the water jacket, said manifold including an enlarged depending portion for connection with the wat-er jacket atthe bottom thereof, a steam and vapor receiving tank disposed internally of an airplane wing or aerofoil of an aircraft, means for connecting the manifold with the receiving tank, a series of perforated condensing pipes projecting from the receiving tank into a condensing chamber within the wing or aerofoil,

Va drain tank, means connecting the condenscludinga depending portion for connection with thewater jacket at the bottom thereof, a steam and vapor receiving tank disposed internally of an airplane wing or aerofoil of an aircraft, means for connecting the manifold with the receiving tank, a series of perforated condensing pipes projecting from the receiving tank into a condensing chamber Within the Wing or aerofoil, a drain tank, means connecting the condensing chamber Withl the drain tank, a circulating pump for returning the contents of the drain tank to the engine Water jacket, means for draining the condensate of the receiving tank into the Water jacket, a supply tank in communication with the. Water jacket, means for delivering the contents of the sup-ply tank to the Water jacket, and a gage-glass and means for indicating the Water level Within the depending manifold portion.

4. A device of the character described including, in combination with the Water jacket of an internal combustion engine, a manifold above the Water jacket, said manifold in cluding a depending portion for connection with the Water jacket at the bottom thereof, a steam and vapor receiving tank disposed internally of an airplane Wing or aerofoil of an aircraft, means for connecting the manifold Withthe receiving tank, a series of perforated condensing pipes projecting from the receiving tank into a condensing chamber Within the Wing or aerofoil, a drain tank, means connecting the condensing chamber with the drain tank, -a circulating pump for returning the contents of the drain tank to the engine Water jacket, means for draining the 4condensate ofthe recelving tank into the Water jacket, a supply tank in communication with the Water jacket, means for delivering the contents of the supply tank to the Water jacket.

5. A cluding, in combination with the of an internal combustion engine, a manifold above the Water jacket, said manifold including a depending portion for connection with the Water jacket at the bottom thereof, a steam and vapor receiving tank disposed internally of an airplane Wing device of the character described in- Water jacket vor aerofoil of an aircraft, means for connecting the manifold with the receiving tank, steam condensing means connected to the receiving tank V4to deliver steam and vapor therefrom into a condensing chamber Withinv the Wing or aerofoil, a drain tank connected to the condensing chamber, a circulating pump for returning the contents of the drain tank to the engine water jacket, means for draining the condensate of the receiving tank into the engine Water jacket, a supply tank for the engine Water jacket, and means for indicating the Water level in the depending manifold portion.

6. A device of the character described including, in combination With the Water jacket of an internal combustion engine, a manifold connected to the top and to the bottom of the Water jacket, a steamand vapor receiving tank disposed internally of an airplane Wing or aerofoil of an aircraft to receive steam and vapor from the Water jacket, means connecting the receiving tank With the Water jacket to return the condensate of the receiving tank to the Water jacket, steam and vapor conL densing means to receive steam and vapor from the receiving tank and to deliver steam and vapor into a condensing chamber within the Wing or aerofoil, a drain tank for the Acondensing chamber, means for delivering the contents of the drain tank to the Water jacket, and a supply tank for the Water jacket'.

7. A device of the character described including, in combination with the Water jacket of an internal combustion engine, a manifold connected to the top and to the bottom of the Water jacket, a steam and vapor receiving tank to receive steam and vapor from the Water jacket. means for returning the con densate of the receiving tank to the Water jacket, steam and vapor condensing means to receive steam and vapor from the receiving tank and deliver the same into a condensing chamber, a drain tank for the condensing chamber, means for delivering the contents of the drain tank to the Water jacket and a source of supply for the Water jacket. v

8. A device of the character described including, in combination Witlithe Water jacket of an internal combustion engine, a steam and vapor receiving tank, means connected to the top and to the bottom of the Water jacket to eHect direct communication between the Water jacketl and the receiving` tank, means independent of said last named means for returning the condensate ofthe receiving tank to the Water jacket, steam and vapor condensing meansto receive steam and vapor from the receiving tank, a drain tank connected to the Water jacket to receive the condensate from said condensing means, and a source of supply for the Water jacket.

9. A device of the character described including, in combination With the Water jacket of an internal combustion engine, a manifold above the Water jacket, said manifold in'-` cluding a depending portion for connection With the Water jacket at the bottom thereof, a baffle for deflecting such Water as mayl accompany the steam and vapor in the manifold into said depending portion, a steam and vapor receiving tank disposed internally of an airplane Wing or aerofoil of an aircraft, means for connecting the manifold with the receiving tank,-steam condensing means connected to the receiving tank to deliver steam and vapor therefrom into a condensing chamber Within the Wing or aerofoil, a drain tank connected to the `condensing chamber, a circulating pump for returning the contents of llll the drain tank to the engine Water jacket, means for draining the condensate of the receiving tank into the engine Water jacket, a supply tank for the engine Water jacket, and means for indicating the Water level in the depending manifold portion.

10. A device of the character described including, in combination With the Water jacket of an internal combustion engine, a manifold above the Water acket, said manifold including a depending portion for connection with the Water jacket at the bottom thereof, a circulating pump for circulating Water through said jacket and said manifold, a steam and vapor receiving tank disposed internally of an airplane Wing or aerofoil of an aircraft, means for connecting the manifold With the receiving tank, steam condensing means connected to the receiving tank to deliver steam and vapor therefrom into a condensing chamber within the Wing or aerofoil, a drain tank connected to the condensing chamber, a cirfculating pump for returning the contents of the drain tank to the engine water jacket, means for draining the condensate of the receiving tank into the engine Water jacket, a supply tank for the engine Water jacket, and

means for indicating the Water level in the j depending manifold portion.

l1. A device of the character described including, in combination with the Water jacket of an internal combustion engine, a manifold above the water jacket, said manifold including a depending portion for connection With the Water jacket at the bottom thereof, a baflie for delecting such Water as may accompany the-steam and vapor in the manifold into said depending portion, a steam and vapor receiving tank disposed internally of an airplane Wing or aerofoil of an aircraft, means for connectirfg the manifold with the vreceiving tank, steam condensing means connected to the receiving tank todeliver steam andvapor therefrom into a condensing chamber Within the Wing or-aerofoil, a drain tank vconnected to the condensing chamber, a circulating pump for returning the contents of the' drain tank to the engine Water acket, means for draining the condensate of the receiving tank into the engine Water jacket, a supply tank for the engine Water acket, means for indicating the Water level in the depending manifold portion and an additional circulating pump arranged be! tween the depending portion of the manifold and the Water jacket.

l2. A device of the character described including, in combination with the Water jacket of an internal combustion engine, a manifold above the Water jacket, said manifold including a depending port-ion for connection with the Water jacket at the bottom thereof, a steam and vapor receiving tank disposed internally of an airplane Wing or aerofoil of an aircraft,

means for connecting the manifold with the receiving tank, steam condensing means connected to the receiving tank to deliver steam and vapor therefrom into a condensing chamber Within the Wing or aerofoil, a drain tank connected to the condensing chamber, a circulating pump for returning the contents of the drain tank to the engine Water jacket, means for draining the condensate of the receiving tank into the engine Water jacket, a supply tank for the engine Water jacket, a hand controlled valve for controlling admission of Water from said supply tank to said Water jacket, and means for indicating the Water level in the depending manifold portion.

In testimony whereof We affix our signatures.

LESTER P. BARLOW. ROBERT G. BREENE 

